CN104081249B - The system and method for turbine on-line checking including non-spherical lens - Google Patents
The system and method for turbine on-line checking including non-spherical lens Download PDFInfo
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- CN104081249B CN104081249B CN201380007501.6A CN201380007501A CN104081249B CN 104081249 B CN104081249 B CN 104081249B CN 201380007501 A CN201380007501 A CN 201380007501A CN 104081249 B CN104081249 B CN 104081249B
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- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B17/00—Systems with reflecting surfaces, with or without refracting elements
-
- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B23/00—Telescopes, e.g. binoculars; Periscopes; Instruments for viewing the inside of hollow bodies; Viewfinders; Optical aiming or sighting devices
- G02B23/24—Instruments or systems for viewing the inside of hollow bodies, e.g. fibrescopes
- G02B23/2476—Non-optical details, e.g. housings, mountings, supports
- G02B23/2492—Arrangements for use in a hostile environment, e.g. a very hot, cold or radioactive environment
-
- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B23/00—Telescopes, e.g. binoculars; Periscopes; Instruments for viewing the inside of hollow bodies; Viewfinders; Optical aiming or sighting devices
- G02B23/24—Instruments or systems for viewing the inside of hollow bodies, e.g. fibrescopes
-
- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B7/00—Mountings, adjusting means, or light-tight connections, for optical elements
- G02B7/02—Mountings, adjusting means, or light-tight connections, for optical elements for lenses
-
- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B7/00—Mountings, adjusting means, or light-tight connections, for optical elements
- G02B7/02—Mountings, adjusting means, or light-tight connections, for optical elements for lenses
- G02B7/028—Mountings, adjusting means, or light-tight connections, for optical elements for lenses with means for compensating for changes in temperature or for controlling the temperature; thermal stabilisation
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- G—PHYSICS
- G03—PHOTOGRAPHY; CINEMATOGRAPHY; ANALOGOUS TECHNIQUES USING WAVES OTHER THAN OPTICAL WAVES; ELECTROGRAPHY; HOLOGRAPHY
- G03B—APPARATUS OR ARRANGEMENTS FOR TAKING PHOTOGRAPHS OR FOR PROJECTING OR VIEWING THEM; APPARATUS OR ARRANGEMENTS EMPLOYING ANALOGOUS TECHNIQUES USING WAVES OTHER THAN OPTICAL WAVES; ACCESSORIES THEREFOR
- G03B17/00—Details of cameras or camera bodies; Accessories therefor
- G03B17/02—Bodies
- G03B17/12—Bodies with means for supporting objectives, supplementary lenses, filters, masks, or turrets
-
- G—PHYSICS
- G03—PHOTOGRAPHY; CINEMATOGRAPHY; ANALOGOUS TECHNIQUES USING WAVES OTHER THAN OPTICAL WAVES; ELECTROGRAPHY; HOLOGRAPHY
- G03B—APPARATUS OR ARRANGEMENTS FOR TAKING PHOTOGRAPHS OR FOR PROJECTING OR VIEWING THEM; APPARATUS OR ARRANGEMENTS EMPLOYING ANALOGOUS TECHNIQUES USING WAVES OTHER THAN OPTICAL WAVES; ACCESSORIES THEREFOR
- G03B17/00—Details of cameras or camera bodies; Accessories therefor
- G03B17/55—Details of cameras or camera bodies; Accessories therefor with provision for heating or cooling, e.g. in aircraft
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04N—PICTORIAL COMMUNICATION, e.g. TELEVISION
- H04N23/00—Cameras or camera modules comprising electronic image sensors; Control thereof
- H04N23/50—Constructional details
- H04N23/555—Constructional details for picking-up images in sites, inaccessible due to their dimensions or hazardous conditions, e.g. endoscopes or borescopes
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04N—PICTORIAL COMMUNICATION, e.g. TELEVISION
- H04N23/00—Cameras or camera modules comprising electronic image sensors; Control thereof
- H04N23/60—Control of cameras or camera modules
- H04N23/68—Control of cameras or camera modules for stable pick-up of the scene, e.g. compensating for camera body vibrations
- H04N23/682—Vibration or motion blur correction
- H04N23/685—Vibration or motion blur correction performed by mechanical compensation
- H04N23/687—Vibration or motion blur correction performed by mechanical compensation by shifting the lens or sensor position
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
- Engineering & Computer Science (AREA)
- Signal Processing (AREA)
- Astronomy & Astrophysics (AREA)
- Multimedia (AREA)
- Aviation & Aerospace Engineering (AREA)
- Lenses (AREA)
- Lens Barrels (AREA)
- Investigating Materials By The Use Of Optical Means Adapted For Particular Applications (AREA)
- Instruments For Viewing The Inside Of Hollow Bodies (AREA)
- Structure And Mechanism Of Cameras (AREA)
- Radiation Pyrometers (AREA)
Abstract
The present invention relates to the optical camera system of detection inside the non-destructive of on-line operation power generation turbine, power generation turbine includes gas-turbine combustion chamber and turbine stage, the elevated operating temperature in more than 600 DEG C (1112 °F) scopes and including burning gases pollutant.Detecting system includes the non-spherical lens that one or more can withstand greater than 600 DEG C of continuous operating temperatures.Non-spherical lens individually or with spherical lens is combined to establish broader visual field, and the lens bayonet socket than only including spherical lens needs less compound lens.The cooling system being incorporated in the detection system is advantageous to continuously run, and is able to suppress the fouling of lens outer surface burning gases.
Description
The cross reference of related application
This application claims simultaneously submit and assigned serial number be 13/362,365, file number be
It is No.2011P12815US, entitled " to include the system and method for the turbine on-line checking of temperature and vibration compensation lenses bayonet socket
(SYSTEM AND METHOD FOR ONLINE INSPECTION OF TURBINES INCLUDING TEMPERATURE
AND V1BRATION COMPENSATING LENS MOUNT) " CO-PENDING U.S. Utility Patent application it is preferential
Power, it is herein incorporated by reference.
Technical field
The optical camera system detected inside the non-destructive of power generation turbine is run the present invention relates to online (online),
Power generation turbine includes gas-turbine combustion chamber and turbine stage, operating temperature in the range of more than 600 DEG C (1112 °F) simultaneously
And including burning gases pollutant.
Background technology
By the way that High Temperature Optical system is combined with high speed camera imaging, infrared ray or visible light line camera system
The critical internal hair of electric generation gas turbine, steam turbine, generator or its relevant device is monitored between it runs on power plant's mid-term
Motivation part.The design of optical system needs to select and combines lens, optical material and related lens installation structure, to carry
For optimal picture quality, while equipment is set to be survived in severe working environment.For example, gas-turbine combustion chamber and turbine
Section includes the high-temperature combustion gas for damaging and polluting lens surface.
Figure 1A and Figure 1B schematically shows known gas turbine 30, and it has compressor section 32, multiple circumferential combustions
Burn room 34 and make the turbine stage 38 that rotary shaft 40 extends there through.Turbine stage 38 includes the fixed wheel blade 42 of row 1, and can revolve
It is connected to the blade 44 of row 1 of axle 40 with turning.Turbine stage 38 includes the fixed blade and rotating vane of continuous alternately row, for example arranges
2 blades 48 of 2 wheel blades 46 and row.Turbine 30 includes multiple detection ports 36,50 and 52, to easily detect internal part.
As shown in Figure 1A, camera detection 55 is coupled to detection port 36 and including optics tube shell 56, optical tube
Housing 56 has observation port 57, and observation port 57 establishes about 30 degree of visual field being aligned with casing center axis.Camera 58
Capture the image by the lens transmission in optics tube shell 56.Camera detection 55 is used to detect in turbine 30, visual field
In visible area-of-interest, such as arrange the leading edge of 1 wheel blade 42.Similarly, camera detection 55' is coupled to detection port
50 and including optics tube shell 56', optics tube shell 56' have observation port 57', and observation port 57' is established and casing center
About 30 degree of visual field of axis normal direction (that is, transverse direction or side view) alignment.Camera 58 is captured by the lens in optics tube shell 56'
The image of transmission.Camera detection 55,55' are used to detect in turbine 30, visible area-of-interest in visual field.So
And as shown in Figure 1B, there was only 30-34 degree through observation port 57' known viewing field of camera, therefore turbine blade can not be captured
The whole width of 44 leading edges.
Work as what the REAL TIME INFRARED THERMAL IMAGE of inner turbine machine part during online turbine is run or visible light were imaged
Preceding optical design has some limitations, and which has limited visual field, maximum operating temperature, picture quality and system operatio cycle.In order to up to
To desired picture quality, conventional optical system needs to use at least one temperature extremes less than 550 DEG C (1022 °F)
Optical material.In addition, spherical lens group of the conventional design using complicated tight spacing, be related to two or more elements to
Correct for optical aberrations (optical aberrations).
Normal optical pipe for camera imaging system is designed by visual field, picture quality and lens bayonet socket (lens
Mount) the hardship of the design trade-offs among system complexity.Bigger hope visual field needs a greater amount of lens, with closer
Lens between spacing.Conversely, the light transmittance of lens reduces with the increase of lens numbers.Compared to being detected in ambient room temperature
The influence of the camera detection used in, these design trade-offs to high temperature detection application in, such as in online combustion gas
There are significantly directly negative effect in the performance of the optical system used in turbine and life-span.More specifically, in order to correct optics
Aberration, conventional optical design are combined with the different glass material with convex surface and concave surface and use spherical lens.Although energy
It is enough to produce remarkable picture quality, but conventional optical design brings some when being used in severe turbine environment and chosen
War.Need a variety of optical materials of the selection with specific but different optics, calorifics and mechanical structure performance：Grasped closest to heat
The melting temperature of about 600 DEG C (1112 °F) should be had by making at least one material of environment.A small number of optical materials can be born
So high temperature is without significantly loss optical property.In order to correct above-mentioned optical aberration, multiple spherical lenses are required
's.Previously known high temperature detecting system optical tube design has used up to six different lens, to produce enough images
Quality.Increase for the desired visual field of detection zone interested broader in turbine also needs to extra lens.
In practice, it is known that scope/visual field of high temperature detecting system optical tube be 34 ° or less.
With the increase of optics inner lens tube quantity, the Machine Design and operation limitation of lens bayonet socket and system are effectively transported
The row life-span becomes challenging.For example, with the increase of lens numbers in bayonet socket, it is more difficult to protect in high-temperature detection application
Lens alignment is held, and Acceptable life is accordingly damaged.
Before maintenance and repair are needed, " hot arc (the hot for uncolled ground on-line monitoring gas turbine
Sections current imaging systems) " are limited to most about 200-300 hours in operability.It has been observed that imaging system
Failure as caused by the progressive abrasion or breakage of various optical elements, the optical element to bear gas turbine heat and shake
It is dynamic.What although engine performance confirmation of this hundreds of hours maintenance time to the short time can be enough, long-term operation is got over
More to need during its whole service life cycle industrially continuously on-line monitoring inner turbine machine part.Gas turbine
It is intended to continuously run between the periodic maintenance cycle.Before the periodic maintenance cycle, the mechano-optical part of camera detection
It can not be removed during gas turbine operation from monitored gas turbine.The typical maintenance conditions cycle of gas turbine is estimated
For 4000 hours every time, generally predominantly detect as 8000 hours every time.Therefore, it is for continuous on-line detection monitoring system key
Keep not understanding running body completely 4000 hours before having an opportunity to be detected and being repaired.So far, increase imaging system to use
The various trials in life-span have caused to improve to hundreds of hours from tens hours limits.
Therefore, a kind of hot environment detecting system for power system turbine etc. is needed in the art, and it can be with
Bear to operate continuously under higher than 600 DEG C (1112 °F), the preferably of up to temperature environment of 1000 DEG C (1832 °F).Additionally need this
A kind of system with increase visual field of sample.Such a system is also needed to, it reduces the individual lenses used in system
Quantity, to reduce design and Operating Complexity.The needs being additionally present of be improve optical delivery efficiency, while keep and preferably
Improve picture quality.In this area, another overall needs are increase high temperature detecting system operation service life, make itself and regular whirlpool
The turbine maintenance maintenance cycle is consistent：Desirably 4000 hours.
The content of the invention
Therefore, jointly or individually, potential purpose of the invention, which is formed, a kind of is used for power system turbine etc.
Hot environment detecting system, it can be with：Withstand greater than the temperature ring of 600 DEG C (1112 °F) and preferably of up to 1000 DEG C (1832 °F)
Continuous operation under border；Increase visual field；The number of individual lenses used in reduction system, to reduce design and complex operation
Property；Improve optical delivery efficiency；Keep, preferably improve picture quality, and increase system operation service life.
These and other objects are realized according to the embodiment of the present invention by a kind of detection means, the detection means
Possess：Housing with observation port；With the non-spherical lens in the housing, the non-spherical lens is by can be
The material continuously run at a temperature of higher than 600 DEG C (1112 °F) is formed.
Embodiments of the present invention further relate to camera detection, and it possesses：Housing with observation port；With installed in
In the housing, the non-spherical lens in the observation port near-end, the non-spherical lens is by can be higher than 600 DEG C
The material continuously run at a temperature of (1112 °F) is formed.Present embodiment is also equipped with spherical lens, the spherical lens installation
It is aligned behind in the housing and with the non-spherical lens.Respective lens are interested with reference to being transmitted in the housing
The image of object, the object of interest are oriented in the visual field established by lens.Camera is connected to the housing, for producing
Pass through the image of lens transmission.
The invention further relates to a kind of method, for the area-of-interest in the gas turbine of vision-based detection operation.The side
Method possesses following steps：Camera detection is provided, it has the housing with observation port.In the system provided, by energy
The non-spherical lens that enough materials continuously run at a temperature of higher than 600 DEG C (1112 °F) are formed is arranged on observation end in housing
The near-end of mouth.It is aligned behind spherical lens is arranged in housing and with non-spherical lens.Respective lens are combined in housing
The image of object of interest is transmitted, the object of interest is oriented in the visual field established by lens.In the system provided,
Camera is connected to housing, for producing the image by lens transmission.The next step of methods described includes：By camera calibration system
System housing observation port is inserted into the detection port of gas turbine.Then, methods described is related to：Produced during turbine is run
The image of area-of-interest in raw gas turbine.
In certain embodiments of the present invention, lens material selects from following group, and the group is by vitreous silica
(fused quartz), fused silica (fused silica), sapphire, spinelle and aluminum oxynitride (aluminum
Oxynitride, AION) form.In some embodiments, the visual field that non-spherical lens is established is more than 34 degree, and in other realities
Apply in mode, at least 50 degree.In some embodiments, described device is further equipped with being limited by the housing, in institute
The cooling port of observation port near-end is stated, and is connected to the pressurized-gas source of the cooling port, for discharging the observation
The gas-pressurized of port near-end.
A kind of camera detection detected for on-line operation electric generation gas turbine combustion chamber and the inside of turbine stage,
Including：
Optical tube, comprising limit inside housing, the housing have distal tip and it is relative with distal tip, be located at
End between camera case and gas-turbine combustion chamber or turbine stage detection port, the distal tip are used to insert combustion gas
In turbine combustion room or turbine stage detection port, the distal tip includes observation port, it is described it is relative with distal tip,
End between camera case and gas-turbine combustion chamber or turbine stage detection port is retained in outside detection port, institute
Detection port is stated suitable for optical coupled with the optical camera in the camera case outside gas turbine engine；
Port is cooled down, is limited by the housing in observation port near-end；
The non-spherical lens of optical imagery is transmitted, in the housing, in the observation port near-end, with combustion gas
Turbine combustion room or turbine stage detection port and it is relative with distal tip, positioned at camera case and gas-turbine combustion chamber
Or the end optical alignment between turbine stage detection port, for by the caused optical imagery in the visual field of non-spherical lens
It is transferred to end relative with distal tip, between camera case and gas-turbine combustion chamber or turbine stage detection port
Portion；Spherical lens, the spherical lens are arranged in the housing and the non-spherical lens and housing and distal tip phase
To, positioned at camera case and gas-turbine combustion chamber or turbine stage detection port between end optical alignment；
Respective lens are oriented in institute with reference to the image that object of interest is transmitted in the housing, the object of interest
State in visual field；
The housing being connected to outside the gas turbine engine it is relative with distal tip, positioned at camera case and combustion
The camera of end between gas turbine combustion chamber or turbine stage detection port, for capturing the optical picture via lens transmission
Picture；
The cooling port pressurized-gas source is connected to, for discharging the gas-pressurized of the observation port near-end, and
The respective lens and enclosure interior at a temperature of higher than 1112 degrees Fahrenheits (600 degrees Celsius) by can continuously transport
Capable material is formed.
Wherein, the material of the non-spherical lens selects from following group, and the group is by vitreous silica, molten silicon
Stone, sapphire, crystalline ceramics spinelle and crystalline ceramics aluminum oxynitride (AION) are formed.
Wherein, the visual field is more than 34 degree.
Wherein, the visual field is at least 50 degree.
The system includes multiple non-spherical lenses, and at least one non-spherical lens from vitreous silica, fused silica by forming
Group in the material that selects form.
The system further comprises the gas turbine with detection port, wherein seeing housing before gas turbine operation
Examine port to be inserted in the detection port, and the system is interested in generation gas turbine during turbine is run
The image in region.
Jointly or individually, the purpose of the present invention and feature can be by those skilled in the art with any combinations or sub-portfolio
It is applied.
Brief description of the drawings
Can be considered by being combined with accompanying drawing it is described in detail below will be readily understood that the teachings of the present invention, wherein：
Figure 1A is the schematic elevational view of the gas turbine detected with known camera detection；
Figure 1B is the schematic plan view along Fig. 1 1B-1B interceptions；
Fig. 2A is the schematic elevational view of known spherical lens；
Fig. 2 B are the schematic elevational views of non-spherical lens of the present invention；
Fig. 3 A are the schematic elevational views for the known camera lens system for including spherical lens heap, are located at lens for being formed
The image of object of interest in visual field (FOV)；
Fig. 3 B are the schematic elevational views for the camera lens system of the present invention for including non-spherical lens of the present invention；
Fig. 4 is the partial cross sectional explanatory view of known lens bayonet socket；
Fig. 5 is the schematic elevational view of the gas turbine detected with camera detection of the present invention；
Fig. 5 A are the schematic plan views along Fig. 5 5A-5A interceptions；
Fig. 6 is the schematic cross section of the optics tube shell of embodiment of the present invention, and wherein image is parallel to tube hub
Axis is shot；
Fig. 7 is the schematic cross section of the lens bayonet socket in Fig. 6 optical tube shell embodiments of the present invention；
Fig. 8 is the perspective view for being compressed axially spring in Fig. 7 lens bayonet sockets of the present invention；
Fig. 9 is the perspective view of the mounting ring in Fig. 7 lens bayonet sockets of the present invention；
Figure 10 is the schematic cross section of another lens bayonet socket in Fig. 6 optical tube shell embodiments of the present invention；
Figure 11 is the schematic cross section of the optics tube shell of another embodiment of the present invention, and wherein image is perpendicular to pipe
Central axis is shot；
Figure 12 is the schematic cross section of the lens bayonet socket of Figure 11 optical tube shell embodiments of the present invention；
Figure 13 is the radial cross-section figure of another embodiment of mounting ring in Figure 12 lens bayonet sockets of the present invention；
Figure 14 is the schematic cross section of another lens bayonet socket in Figure 11 optical tube shell embodiments of the present invention；
Figure 15 is the schematic cross section of the another lens card mouth embodiment of the present invention；
Figure 16 is the schematic cross-sectional elevation for the detecting system of the present invention for including cooling system；
Figure 17 is the detailed schematic cross-sectional elevational view of Figure 16 cooling systems；
Figure 18 is the schematic front perspective view for the detecting system of the present invention for being connected to gas turbine detection port；
Figure 19 is the schematic front perspective view of the detection camera regulating mechanism for focusing of detecting system of the present invention；And
Figure 20 is the block diagram of detecting system of the present invention, including camera detection and associated electrical/Mechatronic control system portion
Part.
In order to make it easy to understand, identical reference is used in the conceived case, to specify each accompanying drawing to share
Similar elements.
Embodiment
After following description is considered, those skilled in the art will readily recognize that, the teachings of the present invention can be with
Easily with the optical camera system of the detection inside the non-destructive of on-line operation power generation turbine, power generation turbine includes
Gas-turbine combustion chamber and turbine stage, it is in the elevated operating temperature of more than 600 DEG C (1112 °F) scopes and including burning
Gas pollutant.Detecting system includes the non-spherical lens that one or more can withstand greater than 600 DEG C of continuous operating temperature.
Non-spherical lens individually or with spherical lens establishes broader visual field in combination, and needs than only including the saturating of spherical lens
The less compound lens of mirror bayonet socket.Be advantageous to operate continuously including cooling system in the detection system, and suppress burning gases
Fouling to lens outer surface.
Non-spherical lens optical system
It is aspherical in order to improve the mechano-optical performance of " heat " detection imaging system and reduce mechanical package complexity
Mirror element -- being preferably made up of fused silica material -- is substituting at least some known conventional spherical lenses elements.It is molten
It is resistant to elevated temperatures optical material to melt silica.Lens surface contours can be by using known Single point diamond turning o manufacturing technology
To manufacture.Sapphire is another potential high temperature application lens material.
As shown in Figure 2 A, the known lens 60 with spherical face 62 are determined by its constant radius completely, and aspherical
Surface need known to multi-parameter equation its shape described.The optical benefits of lens 64 with non-spherical surface 66 are shown in
In Fig. 2 B, the wherein convergence of rays of light to a single point.In the case of spherical lens 60, such as Fig. 2A, the light of light can form mould
Paste, this can reduce picture quality.The array of spherical lens is had only known, such as shown in Fig. 3 A, six spherical lenses
60-60E needs to sharpen fuzzy image.In contrast, non-spherical lens 64A is combined with spherical lens 60' is enough to produce enough
Clearly image.Image checking camera system with the lens array including non-spherical lens adds the system operation life-span.
The total quantity of lens reduces, and causes the reduction of mechanical package complexity in turn.Less component malfunction and/or dislocation
Energetically influence the service life of detecting system.Because the decay between less continuous lens material layer can smaller, lens numbers
Reduction be advantageously attributed to the increase of light transmittance.Fused silica and sapphire aspherical lensmaterial are by 1000 DEG C of company
Operated at a temperature of continuous operating temperature and 1200 DEG C of short-term discontinuous operation.Detecting system visual field can increase to 50 degree, together
When keep acceptable mechanical package complexity horizontal.Known system with spherical lens is limited to 34 degree or smaller regarded
.
Known lens bayonet socket it is restricted
Compared to the typical known detecting system rigid lens bayonette configuration shown in Fig. 4, some realities of present system
The mode of applying is additionally provided with temperature and vibration compensation lenses bayonet socket.In this exemplary known lens bayonet socket, sphere spaced apart is saturating
Mirror 60F-60H is maintained at bayonet socket cylinder by a series of rigid shaped flanges 72 separated, Rigid spacer ring 74,76 and back-up ring 78
Manage in (mount barrel) 70.Due to the different heat expansion rate of bobbin, back-up ring and nonmetallic lens, lens are subjected to dimensional deformation
Stress, them are made easily to be stressed cracking and/or dislocation.
Detecting system is summarized
Fig. 5 is the schematic elevational view of the online gas turbine 30 of the operability detected with camera detection of the present invention.It is special
Not, the leading edge of first row wheel blade 42 is just detected in real time by detecting system 80, while detecting system 80A detection first row turbines
The leading edge of blade 44.Although shown in figure in specification test position while use two detecting systems, the number of detecting system
Amount and its position can change according to the judgement of user.Two corresponding detecting systems respectively have camera case 82, camera case
82 are optically coupled to optics tube shell 84,84A (having multiple lens remained at by lens bayonet socket), and it, which is transmitted, passes through
The image in visual field that observation port 86,86A are established.Observation port 86 in gas turbine detecting system 80 is oriented in optical tube
The distal tip of housing 84, so that its visual field is aligned with the central axis of housing.Observation port 86A is laterally oriented in optical tube
Housing 84A circumference, so as to its visual field perpendicular to its casing center axis with a theta alignment.As shown in figure 5, detection system
The observation port 86A that unites produces the image of the leading edge of turbine blade 44.Compared to 34 ° or more small field of view for being shown in Figure 1A and 1B
(FOV) camera detection 55' known in the art, Fig. 5 A schematically depict the excellent of 50 ° or bigger visual field (FOV)
Point.Compared to the known detecting system with 34 ° or more small angle, more than bigger 50 ° FOV angles allow to detect larger portion of
Area-of-interest (being herein the leading edge of exemplary turbine blade 44).
Optics tube shell and lens bayonet socket
Fig. 6-15 shows optical tube embodiment 84,84A, and the exemplary reality of the lens of the present invention and lens bayonet socket
Apply mode.Reference picture 6, optics tube shell 84 have the observation port 86 being oriented in its distal tip.Distal lens bayonet socket 90
It is maintained at intermediate lens bayonet socket 92 in optics of metals tube shell 84, keeps different lens to construct in turn.As Fig. 7-9 institute
Show, distal tip lens bayonet socket 90 has the metal lens bayonet socket bobbin 100 formed with tubular structure, and it has overall lenses guarantor
Hold flange 102 and surround and capture the inner circumferential 104 of non-spherical lens 106.Although lens bayonet socket 100 surrounds lens 106 completely,
According to the judgement of those skilled in the art, it may be configured to only surround a part for lens.
Non-spherical lens 106 has the preceding surface 108 that abut and keep flange 102, and rear surface 110.Periphery 112 limits
The radial boundaries of lens 106.Abut lens 106 keeps the local configuration of flange 102 and the local configuration phase on preceding surface 108
Match somebody with somebody, so that pressure is symmetrical on lens circumference.Spherical lens 116 is in the relation being spaced apart and alignment with non-spherical lens 106,
And there is preceding surface 118, rear surface 120 and periphery 122.Alignment and interval between lens 106 and 116 is by annular/tubulose
Metal the first mounting ring 114 (Figure 10) is established；Its preceding surface 114A local configuration meets the local wheel in surface 110 after non-spherical lens
Exterior feature, thereafter surface 114B profiles meet the preceding profile of surface 118 of spherical lens.Second tubular metal mounting ring 124 has preceding surface,
The local configuration on surface 120 matches after profile and spherical lens that the preceding surface has.
Each lens 106,116 are circumferentially captured in the inner circumferential 104 of bayonet socket bobbin 100, and extended axially through corresponding
Matching, abut the profile of lens surface and mounting ring, be maintained the desired lens alignment for picture quality, no matter whirlpool
Operation temperature change and vibration in turbine.Compression spring 126 (Figure 10) is biased element, its preceding table in lens 106,116
Apply constant axial force on face and rear surface, no matter the change of temperature and vibration during turbine operation.By this way, thoroughly
Mirror 106,116, retaining ring 114,124 and lens bayonet socket bobbin 100 can experience different axial expansion rate/shrinkage factors, together
When in all these corresponding components keep relative constancy axial biasing force.Compression spring 124 is by electrical discharge machining by cutting
Cut solid stainless steel tube and formed.Other profile spring biased elements can replace compression spring 124.Compression spring first end 128
The second retaining ring 124 is abut, and the second end 130 abuts spring retaining ring 132 of the capture in housing 100.Alternately,
The second end of compression spring 130 can be permanently attached in housing inner circumferential by welding etc., to replace spring retaining ring 132, if
Need to reduce the axial length of distal lens bayonet socket 90.Distal lens bayonet socket 90 also has distal lens bayonet socket observation port
134, it is aligned with the observation port 86 of optics tube shell 84.
As shown in Figure 10, intermediate lens bayonet socket 92 has single non-spherical lens 106', non-spherical lens 106' circumference
Ground capture in lens bayonet socket bobbin 100', and by the first mounting ring 114' together with biased element compression spring 126' again with bullet
Spring retaining ring 132' is axially maintained together.
Transverse direction or side view optical tube 84A embodiments are shown in Figure 11.Laterally observation is realized by prism 150, the light of prism 150
Learn ground bending spectral frequency ripple (for example, infrared or visible spectrum), with the distal lens bayonet socket with non-spherical lens 106A
90A (Figure 12) is aligned, and is aligned with the intermediate lens bayonet socket 92A (Figure 14) with non-spherical lens 106A'.
Exemplary distal lens bayonet socket 90A is shown in Figure 12, and is installed and protected including lens bayonet socket bobbin 152, before lens
Holder 154 is bound to lens bayonet socket bobbin 152.Retainer 154 is connected on non-spherical lens 106A；Abutment surface profile is corresponding
In lens front surface or first surface local configuration.Flexible lens mounting ring 156, which also has, corresponds to lens 106A second surfaces
Or the surface profile on rear surface, and due to compression spring axial bias element 164 and the axialy offset of the application of spring retaining ring 166
Pressure and be connected to vertically on lens.As shown in figure 13, flexible lens mounting ring 156 has wheel rim 158 and away from wheel rim 158
The multiple cantilevered finger things 160 axially protruded.Finger piece 160 has distal contact surface 162, and distal contact surface 162 has
Some profiles correspond to the lens 106A abutted local configuration.Flexible lens mounting ring with the addition of on the lens 106A of abutting
Additional bias force, and the local buckling in lens bayonet socket bobbin 152 can be compensated.Alternately, entity retaining ring, than
The retaining ring such as the lens bayonet socket 90,92 as shown in corresponding Fig. 7 and 10, it can show instead of lens bayonet socket 90A or other
Flexible lens mounting ring 156 in example property embodiment bayonet socket.
In intermediate lens bayonet socket 92A, as shown in figure 14, lens bayonet socket bobbin 152A circumferentially captures lens 106A', and
Lens are remained axially retained between relative flexible lens mounting ring 156A and 156A'.With relative flexible installing ring 156A
Combined with 156A', compression spring 164A applies axialy offset power on lens 106A'.Spring retaining ring 166A is by spring 164A
It is maintained in lens bayonet socket bobbin 152A.
Figure 15 shows the non-spherical lens 106B and spherical lens 116B of two series connection illustrative embodiments, respectively
156B, 156B' and 156B ", 156B " ' are kept by flexible installing ring.Lens 106B and 116B is by spacer sleeve (spacer
Bushing) 168 separation, and circumferentially constrained by corresponding elastic ring set 167,167A, elastic ring set 167,167A
It is arranged between lens periphery and lens bayonet socket bobbin 152B.Compression spring 164B (being shown in which as spiral wire spring) with it is each
Ring combines to the flexible cantilever finger piece of 156B, 156B' and 156B ", 156B " ' upper offset, to maintain on lens 106B and 116B
Bias axial pressure, so as in lens bayonet socket 164B or optical tube 84A structures compensate heat and vibration caused by deform.Metal
Elastic ring set 167 provides extra damping and lens 106B, 116B bending compensation.Compression spring 164B is by threaded bullet
Spring retaining ring 166B is maintained in housing 152B.
Optical tube cools down and lens cleaning
The detecting system of the present invention can use cooling system in addition, and cooling system sprays around the excircle of optics tube shell
Gas-pressurized is penetrated, and guides gas-pressurized to enter the cooling port for being oriented in optical tube observation port near-end.Pressurized-gas source can
Be from turbomachine compressor section shunting compressed air, or any external pressurized air or in power plant it is available its
Its gas source.
With reference to figure 16 and Figure 17, optics tube shell 84 is inserted into the detection port of gas turbine.Pressurized air source 172
It is the main cooling air from gas turbine discharge chamber, gas turbine discharge chamber has the temperature of about 450 DEG C (842 °F), is less than
Environment temperature in 600 DEG C (1112 °F) or higher turbine stage.Main cooling air G1With than turbine stage gas path G6
The higher relative pressure of interior pressure.Cooling air G1Cooling port 169 is flowed through, and along the excircle axle of optics tube shell 84
To flowing downward.Cooling air stream is directed to non-spherical lens 106C by the cooling port 170 formed in optics tube shell 84
And its flexible lens mounting ring 156C near-end and front, then it leave observation port 86, such as gas flow paths G3It is shown.
Cooling air stream G3With than the combustion gas path G in turbine stage6Higher pressure and lower temperature.It is as a result, cold
But gas path G1-G3Heat is sent out from optics tube shell 84, observation port 86 and non-spherical lens 106C, and is
With higher temperature burning gases G6Insulating.Cooling gas G3Separation layer also maintained before non-spherical lens 106C
The contamination-free gas blanket of relative " clean " so that lens are less prone to collection and make polluted membrane (smudging dirty
Contamination film), prevent the pollutant in burning gases.
Detecting system electronic device and operation
The hardware component of camera imaging system 58 for being connected to optics tube shell is shown in Figure 18 and Figure 19.Optical tube and camera
Imaging system 58 by the port flange mounting ring 180 of the known construction of sealing detection port be connected to turbine detection port 36,
50、52.Known image camera 182 is arranged on camera focus drive 184, and camera focus drive 184 has being capable of edge
Known servomotor/position coder 186 of focal length X-direction arrow translation camera.
With reference to figure 20, image control system 190 is powered to camera focusing motor 186 and camera 182, part of the foundation
The startup, stopping and reversion of motor are caused in the focusing activation point information provided by the encoder of motor 186, triggers phase
The shooting image of machine 182, and receive image from camera and be further processed and store.Image control system 190 includes known
Controller 194, it, which is performed, is stored in programmed instruction in memory 196.Controller 194 via bi-directional data path (for example,
Cable and/or the data/address bus for performing ethernet communication protocol) communicated with console controller 200.Exemplary console controller
200 be the personal computer (PC) with processor 202, and processor 202 performs addressable programming in memory 204 and referred to
Order.Known man-machine interface (HMI) 206 communicates with PC, to realize artificial commander, control and monitoring.PC also can be via known
Wireless communication protocol such as Bluetooth protocol is communicated with other HMI devices, such as tablet PC 208.Image control system
It may include data storage device, for storing, handling and achieving the image received from camera 182.
Before gas turbine to be detected is started, by inserting optical tube 84,84A wherein and pacifying port flange
Dress ring 180 is fixed to detection port, and one or more camera detections 80,80A are respectively coupled to it is expected turbine accordingly
Detect port 36,50,52.The cooling gas source 172 of pressurization is around optics tube shell 84,84A and observation port 86,86A
Near-end spray cooling gas.As previously discussed, cooling gas source 172 can obtain from turbomachine compressor section.The sound of camera 182
Ying Yucong image control systems 190 receive trigger command and capture the figure of the area-of-interest in gas turbine internal part
Picture, and the image captured is sent to image control system, to carry out subsequent treatment and archive.
The advantages of detecting system, summarizes
In the camera detection of the present invention advantages below is provided at using aspheric lens elements：
1. increase system operation service life：The quantity of used lens is reduced, and this causes lens bayonet socket mechanical package to be answered
The reduction of polygamy, so as to have a direct impact to system lifetim.
2. improve signal：The reduction of lens reduces overall attenuation, so as to cause increasing of the whole system optical transport to camera
Add.
3. higher temperature operability：Use fused silica or sapphire, or crystalline ceramics, such as spinelle and nitrogen oxidation
Aluminium (AION), to form non-spherical lens and spherical lens, it is allowed to continuously run under 1000 DEG C of higher operating temperatures, and
1200 DEG C of short-term operation.This is an advantage over 400 DEG C of improvement of Known designs more remote.
4. visual field is bigger：Visual field can have while acceptable mechanical package complexity level and picture quality is kept
Increased.The present invention realizes 50 ° of visual field.Known system has 34 ° or smaller of visual field.
Although have been shown herein and be described in detail combine present invention teach that various embodiments, this area
Technical staff can easily design the embodiment of many other changes still with these teachings.
Claims (6)
- It is 1. a kind of for on-line operation electric generation gas turbine combustion chamber and the camera detection of the inside of turbine stage detection, bag Include：Optical tube, comprising limit inside housing, the housing have distal tip and it is relative with distal tip, positioned at camera End between shell and gas-turbine combustion chamber or turbine stage detection port, the distal tip are used to insert gas turbine In combustion chamber or turbine stage detection port, the distal tip includes observation port, it is described it is relative with distal tip, be located at End between camera case and gas-turbine combustion chamber or turbine stage detection port is retained in outside detection port, the inspection Port is surveyed suitable for optical coupled with the optical camera in the camera case outside gas turbine engine；Port is cooled down, is limited by the housing in observation port near-end；The non-spherical lens of optical imagery is transmitted, in the housing, in the observation port near-end, with gas turbine Combustion chamber or turbine stage detection port and it is relative with distal tip, positioned at camera case and gas-turbine combustion chamber or whirlpool End optical alignment between turbine section detection port, for by the caused optical image transmission in the visual field of non-spherical lens To end relative with distal tip, between camera case and gas-turbine combustion chamber or turbine stage detection port； Spherical lens, the spherical lens are arranged on relative with distal tip with the non-spherical lens and housing in the housing , positioned at camera case and gas-turbine combustion chamber or turbine stage detection port between end optical alignment；For respective lens with reference to the image that object of interest is transmitted in the housing, the object of interest is oriented in described regard In；The housing being connected to outside the gas turbine engine it is relative with distal tip, positioned at camera case and combustion gas wheel The camera of end between machine combustion chamber or turbine stage detection port, for capturing the optical imagery via lens transmission；The cooling port pressurized-gas source is connected to, for discharging the gas-pressurized of the observation port near-end, andThe respective lens and enclosure interior at a temperature of higher than 1112 degrees Fahrenheits (600 degrees Celsius) by can continuously run Material is formed.
- 2. system according to claim 1, wherein, the material of the non-spherical lens selects from following group, described Group is made up of vitreous silica, fused silica, sapphire, crystalline ceramics spinelle and crystalline ceramics aluminum oxynitride (AION).
- 3. system according to claim 1, wherein, the visual field is more than 34 degree.
- 4. system according to claim 1, wherein, the visual field is at least 50 degree.
- 5. system according to claim 1, including multiple non-spherical lenses, at least one non-spherical lens is by from tekite The material selected in the group that English, fused silica form is formed.
- 6. system according to claim 1, further comprise the gas turbine with detection port, wherein in gas turbine Housing observation port is inserted in the detection port before operation, and the system generates combustion during turbine is run The image of area-of-interest in gas-turbine.
Applications Claiming Priority (5)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/362,308 US8896661B2 (en) | 2012-01-31 | 2012-01-31 | System and method for online inspection of turbines including aspheric lens |
| US13/362,308 | 2012-01-31 | ||
| US13/362,365 | 2012-01-31 | ||
| US13/362,365 US9366855B2 (en) | 2012-01-31 | 2012-01-31 | System and method for online inspection of turbines including temperature and vibration compensating lens mount |
| PCT/US2013/022929 WO2013116079A1 (en) | 2012-01-31 | 2013-01-24 | System and method for online inspection of turbines including aspheric lens |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104081249A CN104081249A (en) | 2014-10-01 |
| CN104081249B true CN104081249B (en) | 2017-11-24 |
Family
ID=48905702
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201380015644.1A Active CN104204885B (en) | 2012-01-31 | 2013-01-18 | Include temperature and the system and method for vibration compensation lenses bearing for on-line checking turbine |
| CN201380007501.6A Active CN104081249B (en) | 2012-01-31 | 2013-01-24 | The system and method for turbine on-line checking including non-spherical lens |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201380015644.1A Active CN104204885B (en) | 2012-01-31 | 2013-01-18 | Include temperature and the system and method for vibration compensation lenses bearing for on-line checking turbine |
Country Status (6)
| Country | Link |
|---|---|
| EP (2) | EP2810115B1 (en) |
| JP (2) | JP2015508908A (en) |
| KR (2) | KR101650322B1 (en) |
| CN (2) | CN104204885B (en) |
| CA (2) | CA2861445A1 (en) |
| WO (2) | WO2013116006A1 (en) |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9182285B2 (en) * | 2013-08-15 | 2015-11-10 | Siemens Energy, Inc. | Methods regarding optical probe having an inner tube with separable tube sections to house optical elements |
| US9970325B2 (en) | 2015-04-30 | 2018-05-15 | General Electric Company | Jacking assembly for rotor |
| CN105353504A (en) * | 2015-11-02 | 2016-02-24 | 无锡恒腾精密机械有限公司 | Endoscope lens for engines |
| CN107367899B (en) * | 2017-08-21 | 2019-06-14 | 北京航空航天大学 | A system for photographing air film at the leading edge of a turbine blade in a rotating state |
| DE102017218426B3 (en) * | 2017-10-16 | 2019-01-17 | Lufthansa Technik Ag | Apparatus and method for borescope inspection of jet engines |
| CN110824656B (en) * | 2018-08-07 | 2022-05-27 | 宁波舜宇车载光学技术有限公司 | Optical lens and buffer lens and manufacturing method thereof |
| CN110836778A (en) * | 2019-10-14 | 2020-02-25 | 中国北方发动机研究所(天津) | Non-contact real-time measuring system for temperature in diesel engine cylinder |
| CN114002153B (en) * | 2021-11-12 | 2024-11-12 | 西安热工研究院有限公司 | An optical probe fixing device suitable for gas turbine combustion monitoring |
Family Cites Families (32)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2203660A (en) * | 1938-11-08 | 1940-06-04 | Eastman Kodak Co | Objective mount |
| US2808762A (en) * | 1956-06-25 | 1957-10-08 | Bausch & Lomb | Lens mounting means |
| JPS57207209A (en) * | 1981-06-15 | 1982-12-18 | Zeiss Jena Veb Carl | Optical lens mount |
| JPS6070816U (en) * | 1983-10-20 | 1985-05-18 | 三菱電機株式会社 | Lens retention mechanism |
| JPS6185820U (en) * | 1984-11-13 | 1986-06-05 | ||
| US5052782A (en) * | 1989-03-14 | 1991-10-01 | Hughes Aircraft Company | Resilient lens mounting apparatus |
| JPH03200109A (en) * | 1989-12-28 | 1991-09-02 | Tosoh Corp | Lens with metal frame |
| JP3285217B2 (en) * | 1992-04-16 | 2002-05-27 | オリンパス光学工業株式会社 | Endoscope device |
| JPH0710710U (en) * | 1993-07-12 | 1995-02-14 | 旭光学工業株式会社 | Lens holding structure |
| US5670784A (en) * | 1994-08-26 | 1997-09-23 | Ametek Aerospace Products | High temperature gas stream optical flame sensor |
| US6038079A (en) * | 1997-10-09 | 2000-03-14 | Imagyn Medical Technologies, Inc. | Sapphire objective system |
| JPH11337795A (en) * | 1998-05-22 | 1999-12-10 | Canon Inc | Lens barrel |
| JP2000206386A (en) * | 1999-01-11 | 2000-07-28 | Canon Inc | Lens holding device |
| DE19904152A1 (en) * | 1999-02-03 | 2000-08-10 | Zeiss Carl Fa | Assembly of an optical element and a socket |
| JP4610058B2 (en) * | 2000-08-21 | 2011-01-12 | 株式会社Ihi | Cryogenic liquid observation equipment |
| US6449434B1 (en) * | 2001-01-11 | 2002-09-10 | Eastman Kodak Company | Lens displacement or other control using shaped memory alloy driver |
| JP2003215470A (en) * | 2002-12-10 | 2003-07-30 | Asahi Glass Co Ltd | In-furnace observation device |
| JP2005227405A (en) * | 2004-02-10 | 2005-08-25 | Canon Inc | Optical device |
| US7422559B2 (en) * | 2004-06-16 | 2008-09-09 | Ge Inspection Technologies, Lp | Borescope comprising fluid supply system |
| JP2006039319A (en) * | 2004-07-28 | 2006-02-09 | Sumitomo Heavy Ind Ltd | Lens-holding mechanism and lens frame |
| JP2008242310A (en) * | 2007-03-28 | 2008-10-09 | Kyocera Corp | Imaging device |
| US7619728B2 (en) * | 2007-07-26 | 2009-11-17 | General Electric Company | Methods and systems for in-situ machinery inspection |
| GB0724411D0 (en) * | 2007-12-14 | 2008-01-30 | Stfc Science & Technology | Optical sensor |
| JP5073564B2 (en) * | 2008-04-15 | 2012-11-14 | オリンパス株式会社 | Endoscope device for measurement and program |
| JP2010085715A (en) * | 2008-09-30 | 2010-04-15 | Fujinon Corp | Lens assembly |
| US8164761B2 (en) * | 2008-10-24 | 2012-04-24 | Prime Photonics, Lc | Differential focus blade clearance probe and methods for using same |
| US7987712B2 (en) * | 2008-12-10 | 2011-08-02 | Rosemount Aerospace Inc. | High temperature seal assembly for optical sensor |
| KR101814830B1 (en) * | 2009-09-16 | 2018-01-04 | 메디거스 엘티디. | Small diameter video camera heads and visualization probes and medical devices containing them |
| US8184151B2 (en) * | 2009-09-18 | 2012-05-22 | Siemens Energy, Inc. | Flexible imaging fiber bundle monitoring system for combustion turbines |
| US8256297B2 (en) * | 2010-01-05 | 2012-09-04 | General Electric Company | Systems and methods for measuring turbine blade vibratory response |
| US8439630B2 (en) * | 2010-03-19 | 2013-05-14 | Siemens Energy, Inc. | Optical monitoring system for a turbine engine |
| DE102010017049A1 (en) * | 2010-05-21 | 2011-11-24 | R. Stahl Schaltgeräte GmbH | Optical controller for explosion-proof housing, has translucent filling body comprising inner end and outer end, and ignition-breakdown-safe gap provided between inner lens and outer lens and at front side annular surface of filling body |
-
2013
- 2013-01-18 JP JP2014555569A patent/JP2015508908A/en active Pending
- 2013-01-18 WO PCT/US2013/022013 patent/WO2013116006A1/en active Application Filing
- 2013-01-18 KR KR1020147024519A patent/KR101650322B1/en active Active
- 2013-01-18 EP EP13704841.9A patent/EP2810115B1/en active Active
- 2013-01-18 CA CA2861445A patent/CA2861445A1/en not_active Abandoned
- 2013-01-18 CN CN201380015644.1A patent/CN104204885B/en active Active
- 2013-01-24 WO PCT/US2013/022929 patent/WO2013116079A1/en active Application Filing
- 2013-01-24 EP EP13706767.4A patent/EP2810116B1/en active Active
- 2013-01-24 KR KR1020147021149A patent/KR101616661B1/en active Active
- 2013-01-24 JP JP2014555592A patent/JP5985659B2/en active Active
- 2013-01-24 CA CA2861242A patent/CA2861242A1/en not_active Abandoned
- 2013-01-24 CN CN201380007501.6A patent/CN104081249B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CA2861445A1 (en) | 2013-08-08 |
| CN104204885B (en) | 2017-09-29 |
| EP2810115B1 (en) | 2023-05-17 |
| KR101616661B1 (en) | 2016-04-28 |
| CN104204885A (en) | 2014-12-10 |
| EP2810116B1 (en) | 2024-04-10 |
| JP5985659B2 (en) | 2016-09-06 |
| JP2015513630A (en) | 2015-05-14 |
| KR101650322B1 (en) | 2016-08-23 |
| WO2013116006A1 (en) | 2013-08-08 |
| EP2810116A1 (en) | 2014-12-10 |
| KR20140110984A (en) | 2014-09-17 |
| CN104081249A (en) | 2014-10-01 |
| JP2015508908A (en) | 2015-03-23 |
| CA2861242A1 (en) | 2013-08-08 |
| KR20140122265A (en) | 2014-10-17 |
| WO2013116079A1 (en) | 2013-08-08 |
| EP2810115A1 (en) | 2014-12-10 |
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Address after: Florida, USA Patentee after: Siemens energy USA Address before: Florida, USA Patentee before: SIEMENS ENERGY, Inc. |